Gas turbine engines and methods for reducing spool thrust in a combustor section thereof
US12421906B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 18, 2024 |
| Grant date | Sep 23, 2025 |
| Priority date | — |
| Expiry date | Jan 18, 2044 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/283
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Gas turbine engines and methods for reducing spool thrust in a combustor section thereof are provided. The engines include an impeller, a shaft coupled to the impeller, an inner cavity downstream of the impeller, a thrust bearing assembly mechanically coupled to the shaft, a seal assembly having a seal land, and a controller. The controller is configured to detect a loss of oil event to the thrust bearing assembly and, in response, actuate the seal assembly to move the seal land toward a downstream face of the impeller to form a continuous axial seal about the inner cavity, vent gases from the inner cavity to decrease pressure therein to an extent less than an operating gas pressure thereof, and maintain the axial seal and the pressure within the inner cavity and thereby reduce the axial loads on the shaft.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.